CN104630699A - Method for preparing oxidation resistant coating on surface of niobium alloy material - Google Patents
Method for preparing oxidation resistant coating on surface of niobium alloy material Download PDFInfo
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- CN104630699A CN104630699A CN201510041188.9A CN201510041188A CN104630699A CN 104630699 A CN104630699 A CN 104630699A CN 201510041188 A CN201510041188 A CN 201510041188A CN 104630699 A CN104630699 A CN 104630699A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C12/00—Solid state diffusion of at least one non-metal element other than silicon and at least one metal element or silicon into metallic material surfaces
- C23C12/02—Diffusion in one step
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
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Abstract
The invention relates to a method for preparing an oxidation resistant coating on surface of a niobium alloy material, and belongs to the technical field of high-temperature coatings. The method is that the vacuum arc deposition method is carried out to prepare a molybdenum tungsten alloy coating; the vacuum activating pack cementation technology is carried out to prepare a (Mo, W) Si2 composite gradient coating which has the features of molybdenum silicide and tungsten silicide; meanwhile, the silicon diffusion reaction is performed during silicification so as to generate the coating in which a tungsten molybdenum silicide composite coating is used as an antioxidation layer, niobium silicide is used as a medium layer, and niobium trisilicide is used as a transition layer; the antioxidation life of the coating at the temperature of 1800 DEG C reaches 80 hours, the thermal shock lifetime at the temperature from 1800 to room temperature reaches 1500 times; and the high-speed and high-temperature air scouring test shows that the scouring resistance lifetime under the conditions that the air flows at speed of about 1.2km/s and the temperature is 1600 DEG C is 10 hours, and the scouring resistance lifetime at the temperature of 1700 DEG C is 7 hours.
Description
Technical field
The present invention relates to a kind of method preparing oxidation resistant coating on niobium alloy material surface, belong to high temperature coating technical field, particularly relate to a kind of preparation method for precise tracking combustion chamber high temperature oxidation resistant coating.
Background technology
Double elements liquid propellant rail control engine is the important component part of modern space aircraft and strategy and tactics weapon, is widely used in orbits controlling, pose adjustment etc.In recent years, the development of course of new aircraft or weapon, improves constantly the requirement of motor performance, requires that it improves specific impulse, increases room pressure, thus reduces the consumption of propelling agent and alleviate engine weight, and extends engine life or increase strategic weapon range.Thrust chamber allowable temperature is one of principal element determining engine/motor specific impulse, and Thruster material and high-temperature oxidation resistant coating performance then determine working temperature and the scour resistance of thrust chamber.At present, China is applied to space vehicle track and imports and the double elements liquid rocket engine of gesture stability mainly uses the niobium alloy of silicide coating to make Thruster material.For niobium hafnium-silicochromium titanium motor power room, matrix adopts niobium hafnium alloy, and coating process and system are silicochromium titanium coating and the silicochromium titanium hafnium coating of fused slurry, and its working temperature is about 1400 DEG C.
In order to improve the engine jet pipe work-ing life at high temperature of this alloy further, and improve single MoSi
2coating system high-temperature behavior, is improved to compound coating to reach coating and basal body binding force improves by single coating, heat coupling better, reduces Si Elements Diffusion in coating simultaneously, improves the life-span of coating system antioxidant property.
Summary of the invention
The object of the present invention is to provide a kind of method preparing oxidation resistant coating on niobium alloy material surface.
The object of the invention is to be achieved through the following technical solutions.
A kind of method preparing oxidation resistant coating on niobium alloy material surface of the present invention, step is:
The first step: niobium alloy surface molybdenum and tungsten alloy coating preparation
1) prepare negative electrode molybdenum and tungsten alloy target according to rail control motor power chamber shape size, and remove the pollutent of molybdenum and tungsten alloy target material surface, such as oil stain, be then arranged on Vacuum cathodic are deposition equipment, as negative electrode; Vacuum cathodic are deposition equipment is vacuumized, under vacuum the starting the arc is carried out to molybdenum and tungsten alloy target, to remove the impurity on molybdenum target material surface, such as oxide compound;
Described molybdenum and tungsten alloy target content: the content of molybdenum is 80at.%, the content of tungsten is 20at.%;
2) carry out pickling to niobium alloy workpiece surface, its objective is the impurity such as oil stain, oxide compound in order to remove surface, the solution that pickling uses is acid solution, and acid solution comprises nitric acid and sulfuric acid, and the quality proportioning of nitric acid and sulfuric acid is 4:1; Pickling time controlled between 8-10 minute, then used deionized water ultrasonic cleaning, then dried, and was placed in the sample table of Vacuum cathodic are deposition equipment after oven dry, and niobium alloy workpiece and molybdenum and tungsten alloy target distance are 2-10 millimeter; Niobium alloy rail control motor power room workpiece is as anode;
3) to Vacuum cathodic are deposition equipment extracting vacuum, vacuum tightness≤1.33 × 10
-2start during Pa to deposit molybdenum and tungsten alloy coating; Deposition process parameters is: arc current is 60 ~ 100A, coil current 1 ~ 10A; Depositing time is as the criterion with actual needs, ensures that the thickness of molybdenum and tungsten alloy coating is 50 ~ 150 μm;
4) after niobium alloy surface deposition completes, niobium alloy workpiece is cooled to after below 50 DEG C with vacuum chamber, opens vacuum chamber and takes out sample;
Second step: vacuum activating bag oozes preparation (Mo, W) Si
2compound coating
1) mix after silica flour and boron powder being carried out vacuum-drying, mixing adopts ball mill to mix, and obtains mixed powder;
2) by step 1) mixed powder that obtains pours in plumbago crucible, and the sample the first step prepared is imbedded in the mixed powder in plumbago crucible, then plumbago crucible is put into vacuum oven, at 1200 ~ 1350 DEG C of insulation 5 ~ 10h, vacuum tightness≤5 × 10
-2pa; Simultaneously, halide activator is put into activator container for evaporation, the halide activator of evaporation is made to enter in the plumbago crucible of vacuum oven, accelerate the speed of reaction of silica flour and boron powder and molybdenum and tungsten alloy coating, the temperature of container for evaporation is 700 ~ 850 DEG C, thus forms oxidation resistant coating, middle layer, transition layer and matrix by molybdenum and tungsten alloy coating successively to niobium alloy matrix; Oxidation resistant coating is with (Mo, W) Si
2be main, doped with the compound coating of boron; Middle layer is based on niobium disilicide, doped with the compound coating of boron; Transition layer is based on three silication five niobiums, doped with the compound coating of boron; Matrix is niobium alloy;
Be 100 parts of calculating with the quality of silica flour and boron powder, the mass fraction of silica flour is 90-99, and the mass fraction of boron powder is 1-10, and the mass fraction of halide activator is 1-5, and halide activator is sodium-chlor, Sodium Fluoride or Potassium monofluoride;
3) carry out under vacuum being cooled to room temperature, take out product, (Mo, the W) Si finally obtained
2compound coating thickness is 80 ~ 160 μm.
Effect of the present invention is:
The present invention adopts vacuum arc deposition method to achieve the preparation of molybdenum and tungsten alloy coating, and achieves (Mo, W) Si by vacuum activating bag cementation process technology
2the preparation of complex gradient coating, this coating has the characteristic of molybdenum silicide and tungsten silicide, simultaneously in silicatization process, is formed with molybdenum silicide tungsten compound coating as anti oxidation layer by silicon diffusion reaction, middle layer is the middle layer of niobium silicide, the transition layer of transition layer three silicide niobium; This coating anti-oxidant life-span at 1800 DEG C reaches 80 hours, and 1800 DEG C of thermal shock lifetime to room temperature reach 1500 times.Through high-speed and high-temperature airflow scouring test examination, gas velocity is about 1.2km/s, and under 1600 DEG C of conditions, the antiscour life-span is 10 hours, and under 1700 DEG C of conditions, the antiscour life-span is 7 hours.
Under high temperature oxidizing conditions, (M
1, M
2) Si
2– (M
1, M
2, M
3)
5si
3– M
3type multicomponent multiphase system coating system has more excellent high-temperature oxidation resistance, at niobium alloy study of surfaces exploitation molybdenum silicide tungsten compound coating ((Mo, W) Si
2), engine operating temperature can be realized and bring up to 1600-1700 DEG C, there is important impact.
Accompanying drawing explanation
Fig. 1 is the scanning electron microscope schematic diagram of niobium alloy surface molybdenum and tungsten alloy coating cross sections;
Fig. 2 is the structural representation of niobium alloy surface siliconization molybdenum tungsten complex gradient coating;
Fig. 3 is the scanning electron microscope schematic diagram in niobium alloy surface siliconization molybdenum tungsten complex gradient coating cross section.
Embodiment
Below in conjunction with the drawings and specific embodiments, to a kind of niobium alloy material surface high-temp of the present invention anti-oxidant use (Mo, W) Si
2compound coating and preparation method thereof is further described.
Embodiment
Prepare a method for oxidation resistant coating on niobium alloy material surface, step is:
The first step: niobium alloy surface molybdenum and tungsten alloy coating preparation
1) negative electrode molybdenum and tungsten alloy target is prepared according to rail control motor power chamber shape size, molybdenum and tungsten alloy target is trapezoidal right cylinder, lower circular diameter is 45mm, upper circular diameter is 8mm, height is 80mm, and utilize acetone to clean the grunge pollution thing of removing molybdenum and tungsten alloy target material surface, be then arranged on Vacuum cathodic are deposition equipment, as negative electrode; Vacuum cathodic are deposition equipment is vacuumized, under vacuum the starting the arc is carried out to molybdenum and tungsten alloy target, to remove the impurity on molybdenum target material surface, such as oxide compound; In molybdenum and tungsten alloy target, the content of molybdenum is 80at.%, and the content of tungsten is 20at.%;
2) carry out pickling to niobium alloy workpiece surface, its objective is the impurity such as oil stain, oxide compound in order to remove surface, the solution that pickling uses is acid solution, and acid solution comprises nitric acid and sulfuric acid, and the quality proportioning of nitric acid and sulfuric acid is 4:1; Pickling time controlled at 10 minutes, then used deionized water ultrasonic cleaning, then dried, and was placed in the sample table of Vacuum cathodic are deposition equipment after oven dry, and niobium alloy workpiece and molybdenum and tungsten alloy target distance are 2 millimeters; Niobium alloy rail control motor power room is crucial as anode;
3) to Vacuum cathodic are deposition equipment extracting vacuum, vacuum tightness≤3 × 10
-2start during Pa to deposit molybdenum and tungsten alloy coating; Deposition process parameters is: arc current is 80A, coil current 5A; Depositing time is 30min, and the thickness of molybdenum and tungsten alloy coating is 50 μm;
4) after niobium alloy surface deposition completes, niobium alloy workpiece is cooled to after below 50 DEG C with vacuum chamber, and open vacuum chamber and take out sample, the stereoscan photograph of this sample as shown in Figure 1, in Fig. 1, the black color part in top is molybdenum and tungsten alloy layer, and below ash color part is niobium alloy matrix;
Second step: vacuum activating bag oozes preparation (Mo, W) Si
2compound coating
1) mix after 95g silica flour and 5g boron powder being carried out vacuum-drying, mixing adopts ball mill mixing 1h, obtains mixed powder;
2) by step 1) mixed powder that obtains pours in plumbago crucible, and the sample the first step prepared is imbedded in the mixed powder in plumbago crucible, then plumbago crucible is put into vacuum oven, when vacuum tightness reaches 5 × 10
-2during Pa, heat, rate of heating is 15 DEG C/min, and carry out isothermal holding when being heated to 1275 DEG C, soaking time is 10h; Insulation simultaneously, 6g sodium-chlor is put into activator container for evaporation, the sodium-chlor of evaporation is made to enter in the plumbago crucible of vacuum oven, accelerate the speed of reaction of silica flour and boron powder and molybdenum and tungsten alloy coating, the temperature of container for evaporation is 800 DEG C, thus forms oxidation resistant coating, middle layer, transition layer and matrix by molybdenum and tungsten alloy coating successively to niobium alloy matrix; Oxidation resistant coating is with (Mo, W) Si
2be main, doped with the compound coating of boron; Middle layer is based on niobium disilicide, doped with the compound coating of boron; Transition layer is based on three silication five niobiums, doped with the compound coating of boron; Matrix is niobium alloy, as shown in Figure 2;
Be 100 parts of calculating with the quality of silica flour and boron powder, the mass fraction of silica flour is 95, and the mass fraction of boron powder is 5, and the mass fraction of halide activator is 6, and halide activator is Sodium Fluoride; The purity of silica flour is greater than 99.99%, and particle diameter is 0.5-2mm; The purity of boron powder is greater than 99.99%, and particle diameter is 100-300 μm;
3) carry out under vacuum being cooled to room temperature, take out product, as shown in Figure 3, the coating in Fig. 3 is corresponding with the coating in Fig. 2 for the stereoscan photograph of this sample; (Mo, the W) Si finally obtained
2compound coating thickness is 140 μm.
Test the product of preparation, result is as follows:
High-temperature oxidation test, adopts low-voltage and high-current direct-electrifying type of heating, infrared thermometer thermometric; Constant temperature oxidation: test piece 30s is warmed up to 1800 DEG C in still air, is incubated, the time of observed and recorded defective coatings, at 1800 DEG C, the anti-oxidant life-span reaches 80 hours; Thermal shock test: be raised to 1800 DEG C from room temperature 30s, insulation 5min, 30s drop to room temperature, thermal shock number of times during observed and recorded defective coatings, and 1800 DEG C of thermal shock lifetime to room temperature reach 1500 times.
MoSi
2high-temperature oxidation resistant coating, by the Inner Wall of Combustion Chamber Scouring Condition of simulation airspace engine, carries out high-temperature high-speed airflow to this composite coating system and washes away detection.The condition of high-temperature high-speed airflow antioxidant property experiment: under airflow scouring speed is 1.2km/s condition, combustion gases are oxygen and propane, respectively to coating 1600,1700 DEG C are detected, under 1600 DEG C of conditions, the antiscour life-span is 10 hours, and under 1700 DEG C of conditions, the antiscour life-span is 6 hours.
Claims (5)
1. prepare a method for oxidation resistant coating on niobium alloy material surface, it is characterized in that step is:
The first step: niobium alloy surface molybdenum and tungsten alloy coating preparation
1) prepare negative electrode molybdenum and tungsten alloy target according to rail control motor power chamber shape size, and remove the pollutent of molybdenum and tungsten alloy target material surface, be then arranged on Vacuum cathodic are deposition equipment, as negative electrode; Vacuum cathodic are deposition equipment is vacuumized, under vacuum the starting the arc is carried out to molybdenum and tungsten alloy target;
2) carry out pickling to niobium alloy workpiece surface, the solution that pickling uses is acid solution, and acid solution comprises nitric acid and sulfuric acid, and the quality proportioning of nitric acid and sulfuric acid is 4:1; Pickling time is 8-10min, then uses deionized water ultrasonic cleaning, then dries, and is placed in the sample table of Vacuum cathodic are deposition equipment after oven dry, and niobium alloy workpiece and molybdenum and tungsten alloy target distance are 2-10 millimeter; Control engine thrust chamber workpiece is as anode;
3) to Vacuum cathodic are deposition equipment extracting vacuum, vacuum tightness≤1.33 × 10
-2start during Pa to deposit molybdenum and tungsten alloy coating; Deposition process parameters is: arc current is 60 ~ 100A, coil current 1 ~ 10A; The thickness of molybdenum and tungsten alloy coating is 50 ~ 150 μm;
4) after niobium alloy surface deposition completes, niobium alloy workpiece is cooled to after below 50 DEG C with vacuum chamber, opens vacuum chamber and takes out sample;
Second step: vacuum activating bag oozes preparation (Mo, W) Si
2compound coating
1) mix after silica flour and boron powder being carried out vacuum-drying, mixing adopts ball mill to mix, and obtains mixed powder;
2) by step 1) mixed powder that obtains pours in plumbago crucible, and the sample the first step prepared is imbedded in the mixed powder in plumbago crucible, then plumbago crucible is put into vacuum oven, at 1200 ~ 1350 DEG C of insulation 5 ~ 10h, vacuum tightness≤5 × 10
-2pa; Meanwhile, halide activator is put into activator container for evaporation, make the halide activator of evaporation enter in the plumbago crucible of vacuum oven, the temperature of container for evaporation is 700 ~ 850 DEG C;
Be 100 parts of calculating with the quality of silica flour and boron powder, the mass fraction of silica flour is 90-99, and the mass fraction of boron powder is 1-10, and the mass fraction of halide activator is 1-5;
3) carry out under vacuum being cooled to room temperature, take out product, (Mo, the W) Si finally obtained
2compound coating thickness is 80 ~ 160 μm.
2. a kind of method preparing oxidation resistant coating on niobium alloy material surface according to claim 1, it is characterized in that: molybdenum and tungsten alloy target content: the content of molybdenum is 80at.%, the content of tungsten is 20at.%.
3. a kind of method preparing oxidation resistant coating on niobium alloy material surface according to claim 1, is characterized in that: halide activator is sodium-chlor.
4. a kind of method preparing oxidation resistant coating on niobium alloy material surface according to claim 1, is characterized in that: halide activator is Sodium Fluoride.
5. a kind of method preparing oxidation resistant coating on niobium alloy material surface according to claim 1, is characterized in that: halide activator is Potassium monofluoride.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105112857A (en) * | 2015-07-24 | 2015-12-02 | 航天材料及工艺研究所 | Method for preparing iridium-silicide composite coating for engine thrust chamber body |
| CN105385987A (en) * | 2015-10-15 | 2016-03-09 | 厦门理工学院 | High-temperature anti-oxidation layer on metal tungsten surface and manufacturing method of high-temperature anti-oxidation layer |
| CN105780000A (en) * | 2016-05-10 | 2016-07-20 | 航天材料及工艺研究所 | Preparation method for engine combustion chamber and combustion chamber surface composite silicide coating |
| CN105861981A (en) * | 2016-04-28 | 2016-08-17 | 厦门理工学院 | Method for preparing tungsten functional coating on surface of niobium or niobium alloy at low temperature |
| CN107523785A (en) * | 2016-06-21 | 2017-12-29 | 张家港市思杰五金工具有限公司 | Molybdenum-base alloy surface oxidation-resistant coating and preparation method thereof |
| CN110387523A (en) * | 2019-07-15 | 2019-10-29 | 中国科学院上海硅酸盐研究所 | A kind of niobium alloy surface multi-layer graded composite high-temperature oxidation resistant coating and preparation method thereof |
| CN112921293A (en) * | 2021-02-01 | 2021-06-08 | 航天材料及工艺研究所 | High-silicon molybdenum silicide composite gradient coating on inner and outer surfaces of engine thrust chamber body and preparation method thereof |
| CN113025951A (en) * | 2021-03-02 | 2021-06-25 | 南昌大学 | Molybdenum alloy containing antioxidant composite coating and preparation method thereof |
| EP3960719A1 (en) * | 2020-08-28 | 2022-03-02 | Raytheon Technologies Corporation | Environmental barrier coating |
| CN114182251A (en) * | 2021-11-09 | 2022-03-15 | 北京神箭空天科技有限公司 | High-temperature protective coating for jet pipe of aerospace vehicle engine and preparation method and application thereof |
| CN114230323A (en) * | 2021-12-22 | 2022-03-25 | 东海县太阳光新能源有限公司 | Method for manufacturing quartz ceramic crucible |
| CN115505891A (en) * | 2022-09-15 | 2022-12-23 | 核工业理化工程研究院 | Tantalum surface composite coating and preparation method thereof |
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| CN105112857A (en) * | 2015-07-24 | 2015-12-02 | 航天材料及工艺研究所 | Method for preparing iridium-silicide composite coating for engine thrust chamber body |
| CN105112857B (en) * | 2015-07-24 | 2017-08-25 | 航天材料及工艺研究所 | A kind of motor power chamber body portion prepares the method that iridium and silicide combine coating |
| CN105385987A (en) * | 2015-10-15 | 2016-03-09 | 厦门理工学院 | High-temperature anti-oxidation layer on metal tungsten surface and manufacturing method of high-temperature anti-oxidation layer |
| CN105385987B (en) * | 2015-10-15 | 2018-11-13 | 厦门理工学院 | Tungsten surface high-temp anti oxidation layer and preparation method thereof |
| CN105861981A (en) * | 2016-04-28 | 2016-08-17 | 厦门理工学院 | Method for preparing tungsten functional coating on surface of niobium or niobium alloy at low temperature |
| CN105861981B (en) * | 2016-04-28 | 2019-05-28 | 厦门理工学院 | A kind of method that niobium or niobium alloy surface low-temperature prepare tungsten functional coating |
| CN105780000A (en) * | 2016-05-10 | 2016-07-20 | 航天材料及工艺研究所 | Preparation method for engine combustion chamber and combustion chamber surface composite silicide coating |
| CN105780000B (en) * | 2016-05-10 | 2018-05-22 | 航天材料及工艺研究所 | A kind of preparation method of engine chamber surface recombination silicide coating |
| CN107523785A (en) * | 2016-06-21 | 2017-12-29 | 张家港市思杰五金工具有限公司 | Molybdenum-base alloy surface oxidation-resistant coating and preparation method thereof |
| CN110387523B (en) * | 2019-07-15 | 2021-04-16 | 中国科学院上海硅酸盐研究所 | Multilayer gradient composite high-temperature oxidation-resistant coating on surface of niobium alloy and preparation method thereof |
| CN110387523A (en) * | 2019-07-15 | 2019-10-29 | 中国科学院上海硅酸盐研究所 | A kind of niobium alloy surface multi-layer graded composite high-temperature oxidation resistant coating and preparation method thereof |
| EP3960719A1 (en) * | 2020-08-28 | 2022-03-02 | Raytheon Technologies Corporation | Environmental barrier coating |
| US12104503B2 (en) | 2020-08-28 | 2024-10-01 | Rtx Corporation | Environmental barrier coating |
| CN112921293A (en) * | 2021-02-01 | 2021-06-08 | 航天材料及工艺研究所 | High-silicon molybdenum silicide composite gradient coating on inner and outer surfaces of engine thrust chamber body and preparation method thereof |
| CN113025951A (en) * | 2021-03-02 | 2021-06-25 | 南昌大学 | Molybdenum alloy containing antioxidant composite coating and preparation method thereof |
| CN113025951B (en) * | 2021-03-02 | 2022-06-07 | 南昌大学 | Molybdenum alloy containing antioxidant composite coating and preparation method thereof |
| CN114182251A (en) * | 2021-11-09 | 2022-03-15 | 北京神箭空天科技有限公司 | High-temperature protective coating for jet pipe of aerospace vehicle engine and preparation method and application thereof |
| CN114182251B (en) * | 2021-11-09 | 2023-09-12 | 北京神箭空天科技有限公司 | High-temperature protective coating for jet pipe of aerospace vehicle engine as well as preparation method and application thereof |
| CN114230323A (en) * | 2021-12-22 | 2022-03-25 | 东海县太阳光新能源有限公司 | Method for manufacturing quartz ceramic crucible |
| CN114230323B (en) * | 2021-12-22 | 2022-11-18 | 东海县太阳光新能源有限公司 | Method for manufacturing quartz ceramic crucible |
| CN115505891A (en) * | 2022-09-15 | 2022-12-23 | 核工业理化工程研究院 | Tantalum surface composite coating and preparation method thereof |
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